Development Of A Flight Control Software Test Environment Simulation Platform Based On Higale

The flight control software,as the core software of missile guidance control,is the key to measuring the combat capability of the whole weapon system.Its reliability and robustness is directly related to the stability and effectiveness of the missile computer.Therefore,the assessment of the flight control software is the top priority in the whole computer system evaluation.Consider of the characteristics of embedded software,this thesis designs a new flight control software testing environment simulation platform using Higale system.Based on the research of the software testing theory and research at home and abroad,combined with the characteristics of aerospace embedded software,based on the principle of practicability and effectiveness,using HiGale simulation system,the flight control software test environment simulation platform simulates seeker basic function and missile flight process.In this thesis,the following problems have been studied:1)How to provide a common test platform.A common test methodology and equipment can improve the test efficiency of the test environment simulation platform.The test engineer uses same test range for every test software and same implementation for each test item.Test tools and equipment also adopt uniform performance indicators.Thus the test results would be fair and objective.This thesis designs a set of general flight control software through the expansion of general interface setup.Using the traditional missile computer A/D,I/O and RS422 interface uploaded data to Ethernet by Higale simulation system analysised.GJBA289 A interface communicate with Ethernet by universal vertical communication simulator.This thesis design a flight control software test environment simulation platform,in order to save cost and time in the flight control software testing.2)How to validate the correctness of the software local processing.In dynamic test process,local test point only can be tested through black box by comparison of several specified input/ output models and software output.This is because software cannot run online and intermediate variable cannot be collected.This study builds the peripheral system for flight control software,makes it is able to simulate online.During the software testing,firstly find the local features or algorithm’s input and output data points of software being tested.Then according to test requirements,set test data into the input point and save the results of data output point.Finally,the actual data output will be compared with the anticipation of local features or algorithm test to judge whether the software is running correctly.If the comparison results are consistent,it shows the software design is correct.3)How to solve the difficulties in failure mode.The test problem in failure mode can be classified into two kinds: Analog input of software boundary condition and real-time monitoring on the performance of software.Analog input of boundary conditions is easy to be limited by equipment operating conditions.Real-time monitoring can not run in highly integrated equipment.In this thesis,it ensures test case execution in software boundary condition and failure mode through the flexible control of hardware signal,to make the software statement coverage to 100% and the branch coverage also to 100%.Moreover,by simulating flight process,the real-time data of monitoring the flight control software can be recorded.At present,the test platform has been applied to the practical project of mission flight control system.The sample test phase has been completed,453 test cases have been designed,and there is no unused case.This test platform implements all test points which should be tested theoretically,and realizes the artificial intervention and limit situation simulation of the variables involved in the algorithms.Whereas there are only 298 executable cases of flight control software without this platform.